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TsAGI Science Journal

ISSN Imprimir: 1948-2590
ISSN On-line: 1948-2604

TsAGI Science Journal

DOI: 10.1615/TsAGISciJ.2018026350
pages 699-709

CONTROL OF VORTEX FLOW OVER A MANEUVERABLE AIRCRAFT MODEL USING NOSE FLAPS AT LARGE ANGLES OF ATTACK

Konstantin Anatolievich Osipov
Central Aerohydrodynamic Institute (TsAGI), 1 Zhukovsky Str., Zhukovsky, 140180, Moscow Region, Russia

RESUMO

The results of a numerical study of the effect of nose flaps on the longitudinal and lateral aerodynamic characteristics of a maneuverable aircraft model are presented. Analysis of the numerical aerodynamic characteristics and visualization of the flow fields showed that changing the location of the nose flaps along the fuselage may increase the range of linear dependence of the lift coefficient on the angle of attack by Δα ≈ 4° starting from α = 16° as well as increase the lift coefficient and aerodynamic efficiency by ΔK ≈ 0.8 at α = 20°. An increase in the sweep angle due to the extension of the nose flaps located on the front part of the model also leads to an increase in the lift coefficient at large angles of attack and increases the range of the linear dependence of the lift coefficient on the angle of attack by Δα = 8° starting from α = 16° and aerodynamic efficiency by ΔK ≈ 1 at α = 20°. A one-sided extension of the nose flap to generate additional increments of the roll and yaw moments is considered.


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